US 12,084,184 B2
Aerospace vehicles having multiple lifting surfaces
William Tyler Mathews, Springville, AL (US); and Harold Irven Mathews, Jr., Springville, AL (US)
Filed by SE AERONAUTICS INC, Springville, AL (US)
Filed on Oct. 28, 2022, as Appl. No. 18/050,850.
Claims priority of provisional application 63/263,879, filed on Nov. 10, 2021.
Prior Publication US 2023/0143095 A1, May 11, 2023
Int. Cl. B64C 39/08 (2006.01); B64C 1/00 (2006.01); B64C 1/26 (2006.01); B64C 9/24 (2006.01); B64C 23/06 (2006.01); B64D 27/20 (2006.01); B64F 5/10 (2017.01)
CPC B64C 39/08 (2013.01) [B64C 1/26 (2013.01); B64C 9/24 (2013.01); B64C 23/069 (2017.05); B64D 27/20 (2013.01); B64F 5/10 (2017.01); B64C 2001/0072 (2013.01)] 5 Claims
OG exemplary drawing
 
1. An aerospace vehicle comprising:
a fuselage having a fineness ratio of equal to or greater than 8;
a first wing, a second wing, and a third wing coupled to the fuselage, each wing having an aspect ratio of equal to or greater than 35;
at least one stabilizing unit coupled to the fuselage; and
at least one propulsion system;
wherein the first wing includes a leading edge and a first wing root of the first wing;
wherein the second wing includes a leading edge and a first wing root of the second wing;
wherein the third wing includes a leading edge and a first wing root of the third wing;
wherein the first wing is coupled to the fuselage such that the intersections of the first wing leading edge and the first wing root of the first wing is located approximately 26.67% of the fuselage length forward of the intersections of the second wing leading edge and the first wing root of the second wing and approximately 5.00% of the fuselage length above the intersections of the second wing leading edge and the first wing root of the second wing; and
wherein the third wing is coupled to the fuselage such that the intersections of the third wing leading edge and the first wing root of the third wing is located approximately 26.67% of the fuselage length aft of the intersections of the second wing leading edge and the first wing root of the second wing and approximately 3.87% of the fuselage length below the intersections of the second wing leading edge and the first wing root of the second wing.